CN104646578A - Isothermal forging method for titanium alloy whole frame-shaped piece - Google Patents
Isothermal forging method for titanium alloy whole frame-shaped piece Download PDFInfo
- Publication number
- CN104646578A CN104646578A CN201310754334.3A CN201310754334A CN104646578A CN 104646578 A CN104646578 A CN 104646578A CN 201310754334 A CN201310754334 A CN 201310754334A CN 104646578 A CN104646578 A CN 104646578A
- Authority
- CN
- China
- Prior art keywords
- forging
- isothermal
- titanium alloy
- isothermal forging
- pressure
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
Landscapes
- Forging (AREA)
Abstract
An isothermal forging method for a titanium alloy whole frame-shaped piece belongs to the field of a novel material and an advanced manufacturing technology. The invention particularly relates to an isothermal forging forming method for the titanium alloy whole frame-shaped piece. The isothermal forging forming method is characterized by comprising the following steps: step 1, preparing a blank: freely forging a circular rod into a square blank with the ratio of length to width to height of (8-8.5) to (2-2.5) to 1 ; freely forging to at least guarantee that forging is carried out between two phase regions by last fire; step 2, isothermally forging: coating a glass coating on the square blank before isothermal forging; forming an included angle of 10-16 degrees between the square blank and the horizontal plane when the square blank is put into an isothermal forging die, wherein the heating temperature Tbeta is lower than 30-100 DEG C, the temperature of the isothermal forging die is 10-30 DEG C lower than the square blank, and the initial loading speed is not more than 2mm/s; keeping the pressure for 5-10 minutes when a pressure gauge indicates to 8000+/-100 tons; and increasing the pressure to 9500-9700 tons and keeping the pressure for 8-15 minutes.
Description
Technical field
The invention belongs to new material and advanced manufacturing technology field, be specifically related to a kind of isothermal forging manufacturing process of whole titanium alloy frame section.
Background technology
Titanium alloy is a kind of less-deformable alloy, and its flow stress is greater than the common alloys such as aluminium alloy and steel alloy, needs larger load in forging process.The forging of large titanium alloy forging part generally adopts forcing press or counter-blow hammer, and the equipment such as Single arm, steam hammer and pneumatic hammer cannot provide the pressure required for forging large titanium alloy forging.Counter-blow hammer utilizes the high speed impact of hammer to deform to make metal, as easy as rolling off a logly makes metal hot-spot, particularly to the material of the such poor thermal conductivity of titanium alloy, thus affect the structure property of forging; The counter-blow hammer of largest domestic is 100 tons, cannot forge projected area more than 1m
2titanium alloy forging.Adopting common forging mode to forge projected area is 1m
2titanium alloy forging about need 40,000 tons of pressure, and the drop press of largest domestic is 10,000 tons, obviously can not meet.
For large titanium alloy frame section, domestic often taking forges the method that several relatively little forging is welded into a complete heavy forging again.Titanium alloy welding requires strict, and introduced electronic bundle welding equipment although domestic, welding cost is high, and weldment is poorer than solid forging reliability.Common forgings profile is thicker, allowance is large, and titanium alloy belongs to difficult mach metal, not only require the low depth of cut and low cutting speed, and the poor thermal conductivity of titanium alloy, according to the research of Sandvik company, under very low cutting speed, its blade temperature is easy to reach more than 1000 DEG C, very large to tool damage.According to foreign statistic, for complex-shaped common forging part, part is less than 10% with forging quality ratio, and that is the metal of more than 90% is machined removal.Titanium alloy is expensive, and the amount of metal that forging is removed will cause cost of parts to increase considerably too much.
Over nearly three, 40 years, along with more and more higher to the war skill performance requirement of fighter plane, forging ' s block dimension is increasing.Forging projected area is larger, shape is more complicated, and the tonnage of equipment needed thereby is larger.But the tonnage of press can not unrestrictedly increase, and reason is: building large press needs a huge sum of money, and in production process, energy consumption is large, equipment difficult in maintenance, amortization charge is high.Last century the nineties, Man Gedeng Wei company of the U.S. is that (the former has 4.5 ten thousand tons of press for the competition of reply foreign competitors especially French company, the latter has 6.5 ten thousand tons of press), the FMT that the 100000 ton large-scale press that construction is new are new with exploitation has made selection, namely stepping FMT production large forgings is developed, this technology has been widely used on large titanium alloy and high temperature alloy forging, with France have like this in the competition of the country of great tonnage press achieve triumph, ensure that the absolute status at American market.The overall bulkhead forging of a TC4 that Wei, Man Gedeng company produced, heavy 2770kg, projected area 5.53m
2, be Titanium Alloys for Aviation forging maximum in the world up to now.Stepping FMT, except the power that press provides, also separately need provide power to adjust the height of mould, realizes difficulty comparatively large in hot forging, domesticly at present not yet develops similar technology.
Isothermal forging is more novel a kind of FMT, and its feature is: be 1. suitable for molding large Complex Parts.Isothermal forging takes full advantage of the material at high temperature low and superplasticity of resistance of deformation, forge the thin abdomen of high muscle and large forgings very applicable, can avoid/reduce the connected modes such as riveted joint, bolt, be the effective means alleviating construction weight; 2. forging precision is high, and allowance is little.Can save a large amount of precious metal, significantly reduce engine machining period, there is obvious cost advantage in batch postpartum, and as produced, same propeller for turboprop machine part is raw materials used only has 1/3 of ordinary hot die forging; 3. the heating times needed for isothermal forging is few.The forging that common die forging needs 16 fire just can be swaged into, isothermal forging only needs 1 ~ 2 fire, is easier to like this control forging performance.Because isothermal forging rate of deformation is little, so overheated structure when can not produce similar rapid forge.
The Titanium Alloy Isothermal Forgings Applied of largest domestic was once forged by Baosteel special steel company, and its projected area is 0.48m
2, but projected area 1m
2above titanium alloy forging is domestic also not to be set foot in, and Large Unsymmetric frame section difficulty is especially large.
Summary of the invention
The object of the invention is: for Problems existing in above-mentioned background technology, propose a kind of isothermal forging method of whole titanium alloy frame section.
Technical scheme of the present invention is: a kind of isothermal forging method of whole titanium alloy frame section, is characterized in that, comprise step as follows:
The first, base: pole open die forging is grown up: wide: high=(8-8.5): (2-2.5): the square billet of 1, open die forging at least ensures that last fire forges at two-phase section;
The second, isothermal forging: square billet coats glass coating before isothermal die forging process, when placing in isothermal forging mould and level be 10 ~ 16 ° of angles, heating-up temperature is T
β30 ~ 100 DEG C below, isothermal forging mold temperature is lower than square billet 10 ~ 30 DEG C; Original upload speed is no more than 2mm/s, Pressure gauge is indicated to 8000 ± 100 ton hours, pressurize 5 ~ 10 minutes, then pressure is increased to 9500 ~ 9700 tons of pressurizes 8 ~ 15 minutes;
The forging stock machined out of isothermal die forging process in described step 2 is removed middle connecting plate, obtain final forging.
In described step 2, square billet one end and mould one sidewall offset.
Described glass coating is Al
2o
3class.
Advantage of the present invention is: become projected area 1 ~ 1.5m by the direct isothermal die forging process of Nogata base
2forging be domestic and international first time, adopt in this way, production process is relatively simply controlled, reproducible, can solve the problem that the overall frame-shaped construction part of domestic large titanium alloy can not forge, fill up domestic blank.
Accompanying drawing explanation
Fig. 1 is waste base placement schematic diagram in a mold
1-counterdie; 2-die cavity; The waste base of 3-
Fig. 2 is the titanium alloy large-sized whole frame fine forge piece structure chart of certain aircraft rear body TA15
Detailed description of the invention
Below by specific embodiment, also the present invention is described in further detail by reference to the accompanying drawings.
An isothermal forging method for whole titanium alloy frame section, is characterized in that, comprises step as follows:
The first, base: pole open die forging is grown up: wide: the square billet of height=L: W: 1, open die forging at least ensures that last fire forges at two-phase section;
The second, isothermal forging: square billet coats glass coating before isothermal die forging process, when placing and horizontal sextant angle V, heating-up temperature T in isothermal forging mould
1, isothermal forging mold temperature T
2; Original upload speed is no more than v, and pressure rises to S
1, dwell time t
1, then pressure is increased to S
2, dwell time t
2;
The forging stock machined out of isothermal die forging process in described step 2 is removed middle connecting plate, obtain final forging.
In described step 2, square billet one end and mould one sidewall offset.
Described glass coating is Al
2o
3class.
Embodiment is in table 1.
Table 1 embodiment
| Example | L | W | V，° | T1，℃ | T2，℃ | V，mm／s | S 1，t | S 2，t | t 1，min | t 2，min |
| Example 1 | 8 | 2 | 16 | 970 | 950 | 2 | 8000 | 9500 | 6 | 12 |
| Example 2 | 8.5 | 2 | 10 | 900 | 890 | 1.5 | 7900 | 9700 | 10 | 8 |
| Example 3 | 8 | 2.5 | 12 | 950 | 920 | 2 | 8100 | 9500 | 5 | 15 |
Claims (4)
1. an isothermal forging method for whole titanium alloy frame section, is characterized in that, comprises step as follows:
The first, base: pole open die forging is grown up: wide: high=(8-8.5): (2-2.5): the square billet of 1, open die forging at least ensures that last fire forges at two-phase section;
The second, isothermal forging: square billet coats glass coating before isothermal die forging process, when placing in isothermal forging mould and level be 10 ~ 16 ° of angles, heating-up temperature is T
β30 ~ 100 DEG C below, isothermal forging mold temperature is lower than square billet 10 ~ 30 DEG C; Original upload speed is no more than 2mm/s,
Pressure gauge is indicated to 8000 ± 100 ton hours, pressurize 5 ~ 10 minutes, then pressure is increased to 9500 ~ 9700 tons of pressurizes 8 ~ 15 minutes.
2. the isothermal forging method of whole titanium alloy frame section according to claim 1, is characterized in that, the forging stock machined out of isothermal die forging process in step 2 is removed middle connecting plate, obtains final forging.
3. the isothermal forging method of whole titanium alloy frame section according to claim 1, is characterized in that, in step 2, square billet one end and mould one sidewall offset.
4. the isothermal forging method of whole titanium alloy frame section according to claim 1, is characterized in that, described glass coating is Al
2o
3class.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310754334.3A CN104646578A (en) | 2013-12-31 | 2013-12-31 | Isothermal forging method for titanium alloy whole frame-shaped piece |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310754334.3A CN104646578A (en) | 2013-12-31 | 2013-12-31 | Isothermal forging method for titanium alloy whole frame-shaped piece |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN104646578A true CN104646578A (en) | 2015-05-27 |
Family
ID=53238502
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201310754334.3A Pending CN104646578A (en) | 2013-12-31 | 2013-12-31 | Isothermal forging method for titanium alloy whole frame-shaped piece |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN104646578A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105397001A (en) * | 2015-12-02 | 2016-03-16 | 贵州安大航空锻造有限责任公司 | Isothermal forging forming method of titanium alloy complex sheet forged piece |
| CN113680936A (en) * | 2021-08-07 | 2021-11-23 | 中国航空工业集团公司沈阳飞机设计研究所 | Isothermal forging process parameter determination method |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101829749A (en) * | 2008-12-25 | 2010-09-15 | 贵州安大航空锻造有限责任公司 | Approximate isothermal forging method of BT25 two-phase titanium alloy disk forge piece |
| CN102121078A (en) * | 2011-01-20 | 2011-07-13 | 西北工业大学 | Composite preparation method for fine crystal titanium alloy |
| CN102513487A (en) * | 2011-12-16 | 2012-06-27 | 陕西宏远航空锻造有限责任公司 | Method for forging large-size integral titanium alloy frames |
| CN102703183A (en) * | 2012-06-04 | 2012-10-03 | 中国航空工业集团公司北京航空材料研究院 | Surface protection lubricant for titanium alloy die forging process |
| CN102896267A (en) * | 2012-09-28 | 2013-01-30 | 中国航空工业集团公司北京航空材料研究院 | Isothermal forging method of TC17 titanium alloy disc-shaped forge piece |
| CN103014574A (en) * | 2012-12-14 | 2013-04-03 | 中南大学 | Preparation method of TC18 ultra-fine grain titanium alloy |
-
2013
- 2013-12-31 CN CN201310754334.3A patent/CN104646578A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101829749A (en) * | 2008-12-25 | 2010-09-15 | 贵州安大航空锻造有限责任公司 | Approximate isothermal forging method of BT25 two-phase titanium alloy disk forge piece |
| CN102121078A (en) * | 2011-01-20 | 2011-07-13 | 西北工业大学 | Composite preparation method for fine crystal titanium alloy |
| CN102513487A (en) * | 2011-12-16 | 2012-06-27 | 陕西宏远航空锻造有限责任公司 | Method for forging large-size integral titanium alloy frames |
| CN102703183A (en) * | 2012-06-04 | 2012-10-03 | 中国航空工业集团公司北京航空材料研究院 | Surface protection lubricant for titanium alloy die forging process |
| CN102896267A (en) * | 2012-09-28 | 2013-01-30 | 中国航空工业集团公司北京航空材料研究院 | Isothermal forging method of TC17 titanium alloy disc-shaped forge piece |
| CN103014574A (en) * | 2012-12-14 | 2013-04-03 | 中南大学 | Preparation method of TC18 ultra-fine grain titanium alloy |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105397001A (en) * | 2015-12-02 | 2016-03-16 | 贵州安大航空锻造有限责任公司 | Isothermal forging forming method of titanium alloy complex sheet forged piece |
| CN113680936A (en) * | 2021-08-07 | 2021-11-23 | 中国航空工业集团公司沈阳飞机设计研究所 | Isothermal forging process parameter determination method |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN100467156C (en) | Method for smithing GH4169 alloy plate shaped forgeable piece in air at an approximately equal temperature | |
| CN109454188A (en) | Ti55531 titanium alloy large size bar free forging method | |
| CN111069499B (en) | Forging process method for TC18 titanium alloy large-scale binding support forge piece | |
| CN110976727B (en) | Forging method for improving structure uniformity of titanium alloy forging | |
| CN109622868B (en) | Forging method of T-shaped high-temperature alloy bolt forge piece | |
| CN110976747B (en) | Method for forging TC17 alloy blisk through beta forging | |
| CN102581188B (en) | Method for machining TC4-DT titanium alloy large-specification slab forged piece | |
| CN104668417A (en) | Radial forging type strain-induced semi-solid die forging process for outer cylinder forged piece of aircraft landing gear | |
| CN107999687A (en) | A kind of aluminium alloy vane forging and preparation method thereof | |
| CN108044007B (en) | Forging method of high-uniformity Ti632211 titanium alloy plate | |
| CN109622837B (en) | Preparation method and device of TC11 titanium alloy cake blank with high flaw detection level | |
| CN103668027A (en) | Quasi beta forging process for TC25 titanium alloy | |
| CN103962487A (en) | Large-scale solid-forging metal framework with lugs and manufacturing method thereof | |
| CN112264566A (en) | Processing method of large-scale hot-strength titanium alloy forging | |
| CN103341580A (en) | Free forging method for medium-pressure combined regulation valve stem workblank of supercritical turbine | |
| CN112872261A (en) | Forging method of titanium alloy flange plate forge piece | |
| CN112692519A (en) | Forming method of GH4169 alloy large-size special-shaped section outer casing forged piece | |
| CN102019336A (en) | Die forging shaping technology specially used for manufacturing petroleum drilling machine elevator movable wing plates | |
| CN104646578A (en) | Isothermal forging method for titanium alloy whole frame-shaped piece | |
| CN103042144A (en) | Method for forging automobile engine crankshaft | |
| CN102886646A (en) | Process for forging end head of electric upset steel pull rod | |
| CN103878280A (en) | Forging method of ultrahigh strength aluminum alloy | |
| CN113399608B (en) | Forging forming method for TB6 titanium alloy special-shaped connecting piece | |
| CN106391958A (en) | Method for manufacturing TC4 large-sized titanium alloy inclined tube-type die forged piece | |
| RU2381083C1 (en) | Manufacturing method of scapular blanks |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20150527 |
|
| RJ01 | Rejection of invention patent application after publication |